US3857650A - Vaned rotor for gas turbines - Google Patents

Vaned rotor for gas turbines Download PDF

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Publication number
US3857650A
US3857650A US00408335A US40833573A US3857650A US 3857650 A US3857650 A US 3857650A US 00408335 A US00408335 A US 00408335A US 40833573 A US40833573 A US 40833573A US 3857650 A US3857650 A US 3857650A
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US
United States
Prior art keywords
rotor
vanes
coil
vaned
support surface
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US00408335A
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English (en)
Inventor
R Cerrato
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Fiat SpA
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Fiat SpA
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Filing date
Publication date
Application filed by Fiat SpA filed Critical Fiat SpA
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Publication of US3857650A publication Critical patent/US3857650A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding

Definitions

  • ABSTRACT A vaned rotor of the type comprising a central metal hub or rotor body carrying a plurality of rotor blades made of a ceramic material, in which the blades are simply located on the rotor body and held in place by a coil of carbon fibres or ceramic fibres which surrounds the blades.
  • each blade has a transverse part at the radially outer end thereof, which is partly cylindrical and which together with the transverse parts of the other blades, forms a substantially cylindrical support surface for the coil.
  • This invention relates to vaned rotors for gas turbines, and particularly to rotors of the type having a metal body and a number of ceramic vanes attached at the root thereof to the rotor body. Such rotors are particularly suited to operate in gases at a very high temperature.
  • ceramic materials used for such vanes have much better physical properties at high temperatures (i.e., over l,lC than any metal alloy, especially if undergoing compression loads, they are nevertheless very difficult to couple to metal parts because of their relative fragility, lack of ductility, and their low coefficient of expansion.
  • the present invention seeks to provide a vaned rotor for a gas turbine, of the type having a metal rotor body and ceramic vanes, in which the above mentioned inconveniences are overcome.
  • a vaned rotor for a gas turbine of the type comprising a rotor having a metal rotor body and a plurality of ceramic vanes attached to the periphery of the metal body, in which each vane has a transverse part at the radially outer end thereof, the said transverse parts of the vanes together forming a support surface around which is wound a coil of substantially inextensible filaments, the coil acting to absorb the radial forces exerted on the vanes of the rotor during use.
  • FIG. 1 is a view in axial section of part ofa rotor for a gas turbine, formed as an embodiment of this invention; and 1 FIG. 2 is a partial face view of the rotor illustrated in FIG. 1.
  • the periphery 12 of the disc 10 has a number of grooves which extend parallel to the axis of the disc, in which the roots 16 of a number of vanes 18 are located.
  • the shape of the grooves 20 is not important as far as this invention is concerned and can be any suitable shape instead of that shown; for example they could have a which are orthogonal to the grooves 20.
  • the vanes 18 are made of a ceramic material and at the radially outer end each has a transverse portion 22, formed as a part-cylindrical surface coaxial with the disc 10.
  • Each transverse portion 22 is integral with the vane 18 on which it is formed, and is provided with axially spaced, circumferentially extending lateral shoulders or borders 24 and 26.
  • the combined transverse portions 22 of all the vanes 18 forms an effectively continuous cylindrical surface around which is wound a coil 28 formed by filaments of ceramic fibres or carbon fibres having-a high modulus of elasticity.
  • the coil of filaments acts to hold the vanes 18 on the disc 10 and to maintain them in position during operation of the turbine without relying on any form of coupling at the roots of the vanes.
  • the fibres used are sensitive to oxidation they can be protected, during winding of the coil onto the cylindrical surface formed by the transverse parts of the vanes, with a thin layer of liquid ceramic, which after baking will encapsulate the fibres isolating them from the oxidising agents; alternatively metallization before or after the winding operation may be effected.
  • a vaned rotor for a gas turbine of the type comprising:
  • each vane has a transverse part at the radially outer end thereof, said transverse parts of said vanes together forming a support surface
  • each said vane is a partly cylindrical surface, said partly cylindrical surfaces together forming a substantially continuous cylindrical support surface, two lateral shoulders on said radially outer surface of each said transverse part, said shoulders being axially spaced and extending sub stantially circumferentially of said cylindrical surface,

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US00408335A 1972-10-23 1973-10-23 Vaned rotor for gas turbines Expired - Lifetime US3857650A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
IT70323/72A IT975329B (it) 1972-10-23 1972-10-23 Struttura di parti metalliche e nom metalliche statiche o rotanti per ambienti ad alta temperatura particolarmente per rotori e stato ri di turbine a gas

Publications (1)

Publication Number Publication Date
US3857650A true US3857650A (en) 1974-12-31

Family

ID=11313765

Family Applications (1)

Application Number Title Priority Date Filing Date
US00408335A Expired - Lifetime US3857650A (en) 1972-10-23 1973-10-23 Vaned rotor for gas turbines

Country Status (4)

Country Link
US (1) US3857650A (it)
FR (1) FR2204216A5 (it)
GB (1) GB1411316A (it)
IT (1) IT975329B (it)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4011295A (en) * 1974-10-07 1977-03-08 The Garrett Corporation Ceramic rotor for gas turbine engine
US4017209A (en) * 1975-12-15 1977-04-12 United Technologies Corporation Turbine rotor construction
US4580943A (en) * 1980-12-29 1986-04-08 The United States Of America As Represented By The Secretary Of The Army Turbine wheel for hot gas turbine engine
US4767273A (en) * 1987-02-24 1988-08-30 Westinghouse Electric Corp. Apparatus and method for reducing blade flop in steam turbine
WO1999037888A1 (en) * 1998-01-23 1999-07-29 Diversitech, Inc. Shrouds for gas turbine engines and methods for making the same
US6439844B1 (en) * 2000-12-11 2002-08-27 General Electric Company Turbine bucket cover and brush seal
US20100158675A1 (en) * 2008-12-23 2010-06-24 Snecma Turbomachine rotor having blades of composite material provided with metal labyrinth teeth
GB2483495A (en) * 2010-09-10 2012-03-14 Magna Parva Ltd Rotor blade disc, eg for a turbofan engine, having blades supported by an outer ring
US20140301858A1 (en) * 2011-08-15 2014-10-09 Tsinghua University Rotor device, turbine rotor device, and gas turbine and turbine engine having same
GB2521588A (en) * 2013-10-11 2015-07-01 Reaction Engines Ltd Turbine blades

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2475113A1 (fr) * 1980-02-04 1981-08-07 Rockwell International Corp Rotor ceramique pour turbine
DE3842710C1 (it) * 1988-12-19 1989-08-03 Mtu Muenchen Gmbh

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR55020E (fr) * 1946-09-20 1951-06-05 Turbine à gaz à haute température
FR997219A (fr) * 1945-06-16 1952-01-03 Turbine
US3042366A (en) * 1958-05-05 1962-07-03 Holmquist Ernst Rudolf Magnus Axial flow gas turbine
US3095138A (en) * 1957-05-28 1963-06-25 Studebaker Corp Rotating shroud
US3403844A (en) * 1967-10-02 1968-10-01 Gen Electric Bladed member and method for making
US3556675A (en) * 1969-01-29 1971-01-19 Gen Electric Turbomachinery rotor with integral shroud
US3601500A (en) * 1968-08-28 1971-08-24 Rolls Royce Rotor assembly for a fluid flow machine
US3754839A (en) * 1972-05-01 1973-08-28 United Aircraft Corp Filament reinforced rotor assembly

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR997219A (fr) * 1945-06-16 1952-01-03 Turbine
FR55020E (fr) * 1946-09-20 1951-06-05 Turbine à gaz à haute température
US3095138A (en) * 1957-05-28 1963-06-25 Studebaker Corp Rotating shroud
US3042366A (en) * 1958-05-05 1962-07-03 Holmquist Ernst Rudolf Magnus Axial flow gas turbine
US3403844A (en) * 1967-10-02 1968-10-01 Gen Electric Bladed member and method for making
US3601500A (en) * 1968-08-28 1971-08-24 Rolls Royce Rotor assembly for a fluid flow machine
US3556675A (en) * 1969-01-29 1971-01-19 Gen Electric Turbomachinery rotor with integral shroud
US3754839A (en) * 1972-05-01 1973-08-28 United Aircraft Corp Filament reinforced rotor assembly

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4011295A (en) * 1974-10-07 1977-03-08 The Garrett Corporation Ceramic rotor for gas turbine engine
US4076456A (en) * 1974-10-07 1978-02-28 The Garrett Corporation Ceramic rotor for gas turbine engine
US4017209A (en) * 1975-12-15 1977-04-12 United Technologies Corporation Turbine rotor construction
US4580943A (en) * 1980-12-29 1986-04-08 The United States Of America As Represented By The Secretary Of The Army Turbine wheel for hot gas turbine engine
US4767273A (en) * 1987-02-24 1988-08-30 Westinghouse Electric Corp. Apparatus and method for reducing blade flop in steam turbine
US6223524B1 (en) 1998-01-23 2001-05-01 Diversitech, Inc. Shrouds for gas turbine engines and methods for making the same
WO1999037888A1 (en) * 1998-01-23 1999-07-29 Diversitech, Inc. Shrouds for gas turbine engines and methods for making the same
US6439844B1 (en) * 2000-12-11 2002-08-27 General Electric Company Turbine bucket cover and brush seal
US20100158675A1 (en) * 2008-12-23 2010-06-24 Snecma Turbomachine rotor having blades of composite material provided with metal labyrinth teeth
US8870531B2 (en) * 2008-12-23 2014-10-28 Snecma Turbomachine rotor having blades of composite material provided with metal labyrinth teeth
GB2483495A (en) * 2010-09-10 2012-03-14 Magna Parva Ltd Rotor blade disc, eg for a turbofan engine, having blades supported by an outer ring
GB2483495B (en) * 2010-09-10 2013-02-13 Magnaparva Space Ltd Mounting of rotor blades
US20140301858A1 (en) * 2011-08-15 2014-10-09 Tsinghua University Rotor device, turbine rotor device, and gas turbine and turbine engine having same
US10378365B2 (en) * 2011-08-15 2019-08-13 Tsinghua University Rotor device, turbine rotor device, and gas turbine and turbine engine having same
GB2521588A (en) * 2013-10-11 2015-07-01 Reaction Engines Ltd Turbine blades

Also Published As

Publication number Publication date
GB1411316A (en) 1975-10-22
FR2204216A5 (it) 1974-05-17
IT975329B (it) 1974-07-20

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